Aeroplane.



E. CARRET & A. SCHMITT. v

AEROPLAN E. APPLICAT|0N FILED JULY 22 I913.

Patented June 20, 1916.

ETIENNE CARRET ANT) ADRIEN SCI-IMITT, 0F LYON, FRANCE.

AEROPLAN E.

Specification of Letters Patent.

Patented June 20, 1916 Application filed July 22, 1913. Serial No. 780,440. 1

To all whom it may concern Be it known that we, ETIENNE CARRET, a citizen of the French Republic, and ADRIEN SGHMITT, also a citizen of the French Republic, residing at Lyon, France, have in- In the improved aeroplane longitudinal and transverse stability is obtained by means of planes arranged as will hereinafter be described.

The construction of this apparatus is quite different from that of known monoplane aeroplanes, this difference arising from the arrangement of different planes which we term concentrating planes, drift planes and pressure stabilizing planes.

The annexed drawings illustrate the invention in which 7 1 Figure 1 is a plan view of the improved aeroplane. Fig. 2 is a longitudinal section thereof. Fig. 3 is a front view.

The aeroplane which is of the monoplane type, is composed of a triangular keel a on which are arranged at the end the'planes b and b, which we term concentrators. and havin lanes 0 an 0'. Two second planes arranged behind the concentrator planes and termed supporting planes are shown by d and d, and at the back of the devices are the pressure stabilizing planes, f, g and f g, the planes f and f being horizontally disposed and formed integral with the planes 9,9,

which latter are inclined forwardly and downwardly from their horizontal oblique lines of intersections with the horizontal planes at 30 to the, same. I

The apparatus is provided with a rudder k for lateral steering and a rudder i for vertical steering.

The concentrator planes 1) and b are 1nclined laterally and downwardly, Fig. 3, at an angle of 15 degrees with respect to the horizontal upper surface of the keel, a, Fig. 3, and form at the intersection of the side of the keel with the side of said planes an angle which we call concentrating angle. The said planes are for, the purpose of concentrating the currents of air passing rearwardly under the same in the direction as indicated by the arrows in Fig.

at their extremities fdrift 2, and are inclined downward from front to back, orlongitudinally of the keel, at an angle of incidence of 10 degrees, Fig. 2, so as to obtain a sustaining force inferior to the weight of the motor and to utilize these air currents to assure the point of support for the forward longitudinal stability.

The driftplanes. c and c form with the concentrator planes band I), Fig. 1, angles of 10 degrees, Fig. 3.v The inclination of these drift planes has the result of preventing the concentratedair currents, from escaping from underneath the concentrator planes at the sides, Figs. 1 and 3. By this fact the full sustaining power of the air currents is retained. They are projected backward under.- the supporting-planes d and d, Figs. 1 and 3, which are constructed so as to support the Weight of the apparatus and the aviators. These supporting planes have a longitudinal angle of incidence of 5 degrees inclined from the front backward and v I they have a lateral rising inclination of 2Q degrees with respect to the upper surface of the underside of the supporting planes draws currents of free, air which in their turn strike these planes, and are drawn by the concentrated currents of air owing to the greater speed of the latter and are'prev'ented from escaping too quickly at the extreme sides, Figs. 1 and 3. .Thus all their dynamic sustaining force is produced at the center of pressure with the necessary reactions for the sustention and for the longitudinal stability of theseplanes and of the apparatus. The.

longitudinal stability of the apparatus is further assured by two stabilizing pressure planes ,1, g, and f, g, F1g. 1, at the rear end of the keel, which have been described in detail hereinbefore. These stability planes are arranged to. directly receive the flow of the concentrated air currents driven backward from the extreme edges, Fig. 1, of the supporting-planes and maintains the longitudinal stability of the apparatus by the continual friction of these currents on the inclined surfaces of planes 9, g, Fig. 1, thereby maintaining the rear end of ,the apparatus always invariably horizontal to the direction of travel evenwhen the machine is ascending or descending. By the'relative inclination of these planes a vacuum is as it were produced under the horizontal planes f, f having the tendency, by the pressure which it meets on the upper surface,-to lower it and thus support the tail of the apparatus. It is for this purpose that the plane in continuation of this inclined plane is horizontal, its upper surface being scarcely submitted at all to the action of the concentrated currents of air while its lower surface is struck by an upward thrust of the a1r cur-. rents produced by this inclined plane and.

are the two most effective, since they support the weight of the whole apparatus as well as of the aviators and other loads. Comparison can be made to a lever WlllOll v rests on two points of'support to carry two weights, one weight being situated between these two points, one of these two weights being outside one of these points and balare anced by the other weight. This lever will be more stable than another having only a single point of support, the two weights of which, one on each side of this point, provide the balance. In the first case it will require a very great effort to cause the lever to rock, in the second a mere trifle will upset the balance. Finally the third centerof pressure is split up into two areas, one being above the surfaces of the inclined planes to maintain the tail of the apparatus parallel horizontally to the line of movement, and the other above the horizontal plane which is arranged in continuation of said inclined plane.

The concentrator planes 7) and b, Fig. 1,

7 being inclined at 15 degrees; supposing that a side wind strikes the upper surface of one of these planes and tilts the apparatus and even displaces its center of gravity to such a point that the machine could capsize; such event cannot occur with this apparatus, nor even the slip of the wings in a too pronounced curve with regard to the speed acquired. The pressure'of the wind on the surface of theconcentrator plane struck will operate also on the longitudinal surface of the keel situated on the same side as said concentrator plane. The wind in striking the two upper surfaces of the two aforesaid planes, at the same time strikes the underside of the supporting plane situated on the same side as said two planes; this supporting plane having a transverse rising inclina tion of twenty degrees facilitates the capture of the wind while the surface of the concentrator plane has a descending inclination of 15 degrees which exposes its surface to the wind. The surface of this supporting plane is equivalent to the two other planes together. The Wind pressure striking the lower surfaces of the supporting plane in the reverse direction to the two others is balanced and the apparatus keeps its transverse balance. Owing to the pressure which the concentrator plane supports on its upper surface it would have the tendency to give a gyratory movement to the apparatus. In this casethe action of the pressure stabilizing plane opposite to the concentrator plane intervenes and receives on its surface 9 inclined at 30 and on surface h, which is horizontal, a sufiicient pressure to maintain the apparatus parallel to its path. Owing to the fact that the keel is triangular in cross-section and has one of its longitudinal tapers horizontally disposed and uppermost, it will serve as means for re-acting against any lateral slip on the wings, this being efi'ected by the longitudinal, inclined side faces of the keel, which present considerable area of resisting surfaces. The action of the air upon these lowermost, inclined side surfaces of the keel also tends to render these surfaces supporting planes which counteract the strains upon the keel incident with the production of centrifugal force during the speedy flight of the machine.

What we claim as our invention and desire to secure by Letters Patent of the United States is 1. An aeroplane comprising in combination, a triangular keel, a pair of concentrating planes at the forward end of said keel and disposed one on each side thereof, a,

plane on the extremityof each of the aforesaid concentrating planes, a pair of supporting planes arranged one on each side of said keel behind said concentrating planes, stabilizing planes comprising horizontal portions and inclined'portions at the rear end of said keel, means for steering said aeroplane in the lateral direction, means for steering said aeroplane in thevertical direction and means for propelling said aeroplane.

- 2. An aeroplane comprising in combination, a triangular keel, a pair of longitudinally inclined concentrating planes at the forward end of said keel and disposed one on each side thereof, and inclined transversely thereto at an angle of 15 degrees to the upper surface of said keel, a plane on the extremity of each of said concentrating planes and inclined at an acute angle thereto, a pair of supporting planes arranged one on each side of said keel behind said con centrating planes, a pair of stabilizing planes at the rear end of said keel each comprising a horizontal portion and a porspecification in the presence of two wittion inclined thereto, means for steering said nesses.

aeroplane in the lateral direction, means for ETIENNE CARRET.

steering said aeroplane in the vertical direc- ADRIEN SCHMITT. 5 tion and means for propelling said aero- Witnesses:

plane. -GASTON JEAUNIANO,

In witness whereof we have signed this Memos MERMAR. 

